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公开(公告)号：US09836065B2
公开(公告)日：2017-12-05
申请号：US15401893
申请日：2017-01-09
Applicant: SUNLIGHT PHOTONICS INC.
Inventor： Sergey V. Frolov , John Peter Moussouris , Michael Cyrus
IPC: G05D1/10 , G05D1/00 , G05D1/02 , G05D1/06 , G08G7/02 , G08G5/00 , G08G5/04 , G08G5/02 , G08G5/06 , B64C3/56 , B64C29/00 , B64C37/02 , B64C39/02 , B64D1/02
CPC classification number: G05D1/104 , B64C3/56 , B64C29/0016 , B64C37/02 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/088 , B64C2201/102 , B64C2201/128 , B64C2201/143 , B64C2201/145 , B64D1/02 , G05D1/0022 , G05D1/0027 , G05D1/005 , G05D1/0212 , G05D1/0669 , G05D1/102 , G08G5/0008 , G08G5/0013 , G08G5/0017 , G08G5/0021 , G08G5/003 , G08G5/0065 , G08G5/0069 , G08G5/025 , G08G5/045 , G08G7/02 , Y02T50/14
Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.
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182.发明申请公开(公告)号：US20170297712A1
公开(公告)日：2017-10-19
申请号：US14524268
申请日：2014-10-27
Applicant: The Boeing Company
Inventor： Inyoung Daniel Kim , Thomas M. Rose , Dale Waldo
CPC classification number: B64D5/00 , B64C39/024 , B64C2201/082 , B64C2201/102 , B64C2201/122 , B64C2201/146 , F42B15/08 , F42B30/006 , G01S7/003 , G01S13/003
Abstract: A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a radar antenna for bistatic reception of reflected radar pulses. The UAV operates with a flight profile in contested airspace. A tactical fighter aircraft having a radar transmitter for transmitting radar pulses operates with a flight profile in uncontested airspace. A communications data link operably interconnects the UAV and the tactical fighter aircraft, the communications data link transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the fighter aircraft.
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公开(公告)号：US20170291685A1
公开(公告)日：2017-10-12
申请号：US15388396
申请日：2016-12-22
Applicant: Area- I Inc.
Inventor： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
CPC classification number: B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.
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公开(公告)号：US09731820B1
公开(公告)日：2017-08-15
申请号：US15392993
申请日：2016-12-28
Applicant: SWIFT ENGINEERING, INC.
Inventor： Robert Godlasky , Naoto Ogawa , Andrew Streett
CPC classification number: B64D27/02 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/102
Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.
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公开(公告)号：US20170197702A1
公开(公告)日：2017-07-13
申请号：US15471877
申请日：2017-03-28
Applicant: Area- l Inc.
Inventor： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme
CPC classification number: B64C11/28 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/165
Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. The UAVDC may also comprise a foldable propeller blade with a locking mechanism. Foldable propeller blades may have a stowed configuration and a deployed configuration, and the foldable propeller blades may pivot about a hinge to move between configurations. A foldable propeller blade in a deployed configuration may experience forward folding motion due to forces acting upon it. A locking mechanism—for example, a ratchet and pawl—may lock a foldable propeller blade into a configuration. In a locked arrangement, a UAVDC may comprise at least one foldable propeller that locks into place to prevent forward folding tendency.
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Patent Agency Ranking
公开(公告)号：US20170174342A1
公开(公告)日：2017-06-22
申请号：US14737702
申请日：2015-06-12
Applicant: Deng Huang
Inventor： Deng Huang
CPC classification number: B64C29/0033 , B64C29/02 , B64C39/08 , B64C2201/088 , B64C2201/102
Abstract: A tilt wing aircraft has a spaced plurality of wings mounted on a fuselage to pivot in unison about corresponding ones of a parallel plurality of tilt axes, between an upright position and a cruise position. In the cruise position the wings are disposed edge to edge with a gap less than the width of any of the plurality of wings, as measured at the fuselage. A plurality of power units are mounted on one or more of the wings to rotate in unison with them between a vertical propulsion position and a forward propulsion position. Said plurality of power units can rotate into the vertical propulsion position as the wings rotate into the upright position. The wings are placed in an upright position with the power units positioned to provide vertical propulsion. When powered, the power units can create a downdraft between the wings in order to lift the fuselage. The wings and the power units are rotated to reduce their angles of attack and facilitate forward motion of the fuselage.
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公开(公告)号：US20170166305A1
公开(公告)日：2017-06-15
申请号：US15175161
申请日：2016-06-07
Applicant: Paul E. Arlton , David J. Arlton
Inventor： Paul E. Arlton , David J. Arlton
IPC: B64C27/605 , B64C39/02 , B64C27/14 , B64C27/10
CPC classification number: B64C27/605 , B64C7/00 , B64C27/10 , B64C27/14 , B64C39/024 , B64C2027/8236 , B64C2027/8281 , B64C2201/027 , B64C2201/042 , B64C2201/082 , B64C2201/102 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/201 , B64C2201/203 , B64C2201/205
Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.
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公开(公告)号：US20170115668A1
公开(公告)日：2017-04-27
申请号：US15401893
申请日：2017-01-09
Applicant: SUNLIGHT PHOTONICS INC.
Inventor： SERGEY V. FROLOV , JOHN PETER MOUSSOURIS , MICHAEL CYRUS
CPC classification number: G05D1/104 , B64C3/56 , B64C29/0016 , B64C37/02 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/088 , B64C2201/102 , B64C2201/128 , B64C2201/143 , B64C2201/145 , B64D1/02 , G05D1/0022 , G05D1/0027 , G05D1/005 , G05D1/0212 , G05D1/0669 , G05D1/102 , G08G5/0008 , G08G5/0013 , G08G5/0017 , G08G5/0021 , G08G5/003 , G08G5/0065 , G08G5/0069 , G08G5/025 , G08G5/045 , G08G7/02 , Y02T50/14
Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.
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公开(公告)号：US09616997B2
公开(公告)日：2017-04-11
申请号：US14944482
申请日：2015-11-18
Applicant: Aurora Flight Sciences Corporation
Inventor： Robert Parks , Adam Woodworth , Tom Vaneck , Justin McClellan
CPC classification number: B64C37/00 , B60F5/02 , B63G8/001 , B63G8/08 , B63G2008/005 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/08 , B64C2201/102 , B64C2201/127 , B64C2201/165 , B64C2201/167 , F42B15/20
Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.
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公开(公告)号：US09555873B1
公开(公告)日：2017-01-31
申请号：US15092237
申请日：2016-04-06
Applicant: Area- I Inc.
Inventor： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
CPC classification number: B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.
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